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Journal articles on the topic 'Gas Turbine Engine Control'
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1
Niculescu, Filip, Claudia Borzea, Adrian Savescu, Andrei Mitru, and Mirela Letitia Vasile. "Automation and Electronic Control of Marine Gas Turbine Engine for Ship Revamp." Technium: Romanian Journal of Applied Sciences and Technology 2, no. 4 (June 10, 2020): 98–108. http://dx.doi.org/10.47577/technium.v2i4.923.
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Gas turbines used in propulsion ensure increased efficiency and safety, with a very good power / weight ratio and with low maintenance and operation costs. Due to becoming out-of-date and reaching the maximum operation hours and expected lifetime, which can cause malfunctioning, older turbine engines on frigates need to be replaced with newer generation propulsion engines. The paper presents the replacement of the turbine engine on a defence frigate, focusing on the automation and electronic control solution employed for a propulsion turbine, integrating state-of-the-art techniques. The electronic system ensures control, monitoring and alarm functions, including overspeed protection. A local control panel interfacing the PLC displays the operating parameters and engine controls, also providing maintenance and calibration sequences. The proposed solution enables both the local and the remote control of the ship’s gas turbine.
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Tovkach, Serhii. "CUDA-інтеграція контурів керування авіаційного газотурбінного двигуна." Aerospace Technic and Technology, no. 6 (November 27, 2023): 31–39. http://dx.doi.org/10.32620/aktt.2022.6.04.
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The problem of accelerating the process of designing aircraft gas turbine engines and their control systems, the system "AIRCRAFT-AVIATION ENGINE-FUEL", and forming the technical type of an aircraft engine, adapting to new operating conditions within the framework of experimental design bureaus (EDB) and the industry is using automated systems with low computing performance and incomplete description. Information technologies for developing engines allow duplication and mismatch of data, loss of information and time during transmission and processing for making parametric and structural decisions. To better adaptation of the characteristics of an aviation engine (AE) to the tasks solved by an aircraft in flight, it is necessary to integrate control systems. Integrated control systems are especially effective for managing today's multi-mode aircraft. On the basis of their control, optimal control programs for the power plant (PP) are formed using the criteria for evaluating the effectiveness of the aircraft. This article proposes a paradigm for building integrated control loops for an aircraft gas turbine engine, which can be formed by automating control processes, an automatic control system, and combined control programs. The objective of this research is the processes of constructing adaptive control loops for aircraft gas turbine engines. The subject of this study is the adaptive control of aircraft gas turbine engines using embedded control loops and CUDA architecture. The goal is to improve the dynamic characteristics of an aircraft gas turbine engine through adaptive control using control loops, considering various aircraft flight modes and engine operating modes. Objectives: to determine the main controllable elements of an aircraft engine, adjustable parameters and factors for constructing control loops according to the principle of adaptation; describe the mechanism of joint management of gas turbine engines; to study the processes of building an integration circuit "aircraft - power plant" and develop the concept of an integrated ACS; define the CUDA paradigm for parallel computing of control loops. Conclusions. The scientific novelty lies in the formation of a paradigm for developing adaptive control models for gas turbine engines, considering different aircraft flight modes and engine operation modes.
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Kerr, L. J., T. S. Nemec, and G. W. Gallops. "Real-Time Estimation of Gas Turbine Engine Damage Using a Control-Based Kalman Filter Algorithm." Journal of Engineering for Gas Turbines and Power 114, no. 2 (April 1, 1992): 187–95. http://dx.doi.org/10.1115/1.2906571.
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A second-generation Kalman filter algorithm is described that has sufficient accuracy and response for real-time detection and estimation of gas turbine engine gas path damage caused by normal wear, mechanical failures, and ingestion of foreign objects. The algorithm was developed for in-flight operation of aircraft engines but also has application for marine and industrial gas turbines. The control measurement and microcomputer requirements are described. The performance and sensitivity to engine transients and measurement errors is evaluated. The algorithm is demonstrated with actual engine data of ice and bird ingestion tests.
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Sylvestre, R. A., and R. J. Dupuis. "The Evolution of Marine Gas Turbine Controls." Journal of Engineering for Gas Turbines and Power 112, no. 2 (April 1, 1990): 176–81. http://dx.doi.org/10.1115/1.2906158.
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The background and evolution of gas turbine fuel controls is examined in this paper from a Naval perspective. The initial application of aeroderivative gas turbines to Navy ships utilized the engine’s existing aircraft fuel controls, which were coupled to the ship’s hydropneumatic machinery control system. These engines were adapted to Naval requirements by including engine specific functions. The evolution of Naval gas turbine controllers first to analog electronic, and more recently, to distributed digital controls, has increased the system complexity and added a number of levels of machinery protection. The design of a specific electronic control module is used to illustrate the current state of the technology. The paper concludes with a discussion of the further need to address the issues of fuel handling, metering and control in Navy ships with particular emphasis on integration in the marine environment.
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Tovkach, Serhii. "Control Laws of the Aviation Gas Turbine Engine." Electronics and Control Systems 2, no. 72 (September 23, 2022): 20–25. http://dx.doi.org/10.18372/1990-5548.72.16938.
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The article is devoted to the solution of an important scientific and applied problem of improving the dynamic characteristics of an aviation engine and ensuring flight safety and the efficiency of aircraft operation, taking into account the properties of adaptive control of an aviation gas turbine engine: <structure><functioning><adaptation><development>. Based on the concept of creating perspective aviation engines with an increased level of control automation and with units operating at elevated temperatures and protected from high-energy electromagnetic radiation, the basic laws of controlling an aviation gas turbine engine in throttle modes, low-throttle mode, gas intake and discharge modes, and start-up mode are defined. To improve the working process of the engine, it is proposed to use the gas turbine engine control system as a mechatronic system based on the principle of adaptation. With the help of the Laplace transformation, the dynamic characteristics of the power plant were determined and the mathematical model of the power plant was investigated as a constructive aspect of the automatic control system. The gas turbine and the supersonic air manifold can to some extent be considered as independent control objects, replacing the connections between them with disturbing influences. For the control and limitation circuits, it is necessary to create control programs that calculate the values of the control parameters of the turbocharger rotor speed and gas temperature behind the turbine. Regulation of fuel consumption is carried out according to the derivative of the control parameters.
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Wright, W. E., and J. C. Hall. "Advanced Aircraft Gas Turbine Engine Controls." Journal of Engineering for Gas Turbines and Power 112, no. 4 (October 1, 1990): 561–64. http://dx.doi.org/10.1115/1.2906205.
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With the advent of vectored thrust, vertical lift, and fly-by-wire aircraft, the complexity of aircraft gas turbine control systems has evolved to the point wherein they must approach or equal the reliability of current quad redundant flight control systems. To advance the technology of high-reliability engine controls, one solution to the Byzantine General’s problem (Lamport et al., 1982) is presented as the foundation for fault tolerant engine control architecture. In addition to creating a control architecture, an approach to managing the architecture’s redundancy is addressed.
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Кулик, Микола Сергійович, Володимир Вікторович Козлов, and Лариса Георгіївна Волянська. "AUTOMATION CONTROL SYSTEM OF TECHNICAL CONDITION OF GAS TURBINE ENGINE COMPRESSOR." Aerospace technic and technology, no. 8 (August 31, 2019): 121–28. http://dx.doi.org/10.32620/aktt.2019.8.18.
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The article is devoted to one of the approaches to the construction of an automated system for solving the problems of diagnostics and monitoring of the flow duct of aircraft gas turbine engines and gas turbine plants. Timely detection of faults and subsequent monitoring of their development in operation are possible thanks to automated systems for assessing the technical condition of engines. This is particularly relevant in operating conditions as the knowledge of the technical condition of the engine is necessary in any engine maintenance system allows to choose the content and timing of maintenance, repair of the flow duct of gas turbine engines and gas turbine plants, as well as commissioning. The engineering technique, which can be applied at performance of maintenance and at stages of tests and debugging of aircraft engines, is considered. The automated system implements a method of measuring the air flow through the compressor and a technique for assessing the technical condition of the compressor by the relative change in air flow. To determine the air flow rate through the gas turbine engine, it is sufficient to measure only static pressure values in the flow part. The static pressure receivers are not located in the flow part and do not obscure it, and thus do not affect the compressor gas dynamic stability margin. The inspection area is selected for measuring in the flow duct of the air intake. Static pressure in the maximum and minimum cross sections of the chosen area is measured; the maximum cross-section area of the flow duct, the total temperature of the air flow is measured outside the air intake. To determine the air flow rate, the functional dependence of the air flow rate on the static pressure is used. The algorithm for monitoring and diagnosing the operating condition of the engine is based on a comparison of the actual values of air flow rate with the air flow rate determined during the control tests or when using a mathematical model adapted for this gas turbine engine. The positive effect of the using of the proposed automated control system of technical condition is that the air flow rate measured under operating conditions will significantly increase the objectivity of the control of the operation and technical condition of the gas turbine engine.
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Al-Hamdan, Qusai Z., and Munzer S. Y. Ebaid. "Modeling and Simulation of a Gas Turbine Engine for Power Generation." Journal of Engineering for Gas Turbines and Power 128, no. 2 (April 27, 2005): 302–11. http://dx.doi.org/10.1115/1.2061287.
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The gas turbine engine is a complex assembly of a variety of components that are designed on the basis of aerothermodynamic laws. The design and operation theories of these individual components are complicated. The complexity of aerothermodynamic analysis makes it impossible to mathematically solve the optimization equations involved in various gas turbine cycles. When gas turbine engines were designed during the last century, the need to evaluate the engines performance at both design point and off design conditions became apparent. Manufacturers and designers of gas turbine engines became aware that some tools were needed to predict the performance of gas turbine engines especially at off design conditions where its performance was significantly affected by the load and the operating conditions. Also it was expected that these tools would help in predicting the performance of individual components, such as compressors, turbines, combustion chambers, etc. At the early stage of gas turbine developments, experimental tests of prototypes of either the whole engine or its main components were the only method available to determine the performance of either the engine or of the components. However, this procedure was not only costly, but also time consuming. Therefore, mathematical modelling using computational techniques were considered to be the most economical solution. The first part of this paper presents a discussion about the gas turbine modeling approach. The second part includes the gas turbine component matching between the compressor and the turbine which can be met by superimposing the turbine performance characteristics on the compressor performance characteristics with suitable transformation of the coordinates. The last part includes the gas turbine computer simulation program and its philosophy. The computer program presented in the current work basically satisfies the matching conditions analytically between the various gas turbine components to produce the equilibrium running line. The computer program used to determine the following: the operating range (envelope) and running line of the matched components, the proximity of the operating points to the compressor surge line, and the proximity of the operating points at the allowable maximum turbine inlet temperature. Most importantly, it can be concluded from the output whether the gas turbine engine is operating in a region of adequate compressor and turbine efficiency. Matching technique proposed in the current work used to develop a computer simulation program, which can be served as a valuable tool for investigating the performance of the gas turbine at off-design conditions. Also, this investigation can help in designing an efficient control system for the gas turbine engine of a particular application including being a part of power generation plant.
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Zhang, Tian Gang, and Xiao Yun Hou. "NOx Emission Control in Gas Turbines." Applied Mechanics and Materials 66-68 (July 2011): 319–21. http://dx.doi.org/10.4028/www.scientific.net/amm.66-68.319.
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The increase, in recent years, in the size and efficiency of gas turbines burning natural gas in combined cycle has occurred against a background of tightening environmental legislation on the emission of nitrogen oxides. The higher turbine entry temperatures required for efficiency improvement tend to increase NOX production. To reduce NOX emissions, new engine core configurations with heat management and active systems, as well as advanced combustor technology, have to be investigated. This paper reviews the various approaches adopted by the main gas turbine manufacturers which are achieving low levels of NOX emission from natural gas combustion.
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Kazhaev, V. P., D. Y. Kiselev, and Y. V. Kiselev. "DIAGNOSTIC MODEL OF HELICOPTER TURBOSHAFT ENGINE." Izvestiya of Samara Scientific Center of the Russian Academy of Sciences 25, no. 1 (2023): 99–106. http://dx.doi.org/10.37313/1990-5378-2023-25-1-99-106.
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The article presents a qualitative assessment of the impact on the engine components characteristics of the malfunction occurrence in the flow part of the aviation gas turbine engines, which lead to changes in its geometry. Using the example of a compressor, it is shown that when defects appear in it, two of its characteristics are deformed: efficiency and pressure characteristics (which is confirmed by a significant number of studies). It is concluded that in order to reliably diagnose aviation gas turbine engines by thermogasodynamic parameters, the mathematical model must take into account the change in two characteristics for each engine component of the flow part (and not only the change in the characteristics of the efficiency of the nodes). A linear mathematical model of a helicopter turboshaft turbine engine is presented and the results of calculating the influence coefficient for a given control law are presented. The peculiarity of the presented model is that the state of each engine component is characterized by two state parameters: for compressors, this is the head characteristic and the efficiency characteristic, for turbines, performance characteristics and efficiency.
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Cruz-Manzo, Samuel, Vili Panov, and Chris Bingham. "GAS turbine sensor fault diagnostic system in a real-time executable digital-twin." Journal of the Global Power and Propulsion Society 7 (March 9, 2023): 85–94. http://dx.doi.org/10.33737/jgpps/159781.
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In this study, a sensor fault diagnostic system to detect/isolate and accommodate faults in sensors from an industrial gas turbine has been developed. The sensor fault diagnostic module is integrated with a gas turbine real-time executable digital-twin (RT xDT) reported in a previous study. The sensor fault diagnostic module of the digital-twin considers analytical sensor redundancy using a reference engine model to provide redundant estimates of measured engine variables. A Software-in-the-Loop (S-i-L) architecture and Hardware-in-the-Loop (H-i-L) facility are constructed to assess the sensor diagnostic module (fault detection/ fault isolation) during failure in sensors from the engine. The results demonstrated that if the discrepancy between virtual measurement (provided by digital-twin) and sensor measurement exceeds the prescribed tolerance levels, the sensor fault diagnostic logic determines the state of switching between the virtual and engine sensor measurements in a dual lane control configuration of the gas turbine control system. The sensor fault detection system implemented in the gas turbine RT xDT can be deployed onto a distributed control system of industrial gas turbines to diagnose sensor deficiencies and ensure continuous and safe operation of the gas turbine. Consequently, the developed system will increase engine availability and reliability by diagnosing engine operational deficiencies before severe failure.
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Єнчев, Сергій Васильович, and Сергій Олегович Таку. "Інтелектуальний регулятор запасу газодинамічної стійкості компресора авіаційного ГТД." Aerospace technic and technology, no. 4 (August 27, 2021): 48–52. http://dx.doi.org/10.32620/aktt.2021.4.07.
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The gas-dynamic stability of compressors of aircraft gas turbine engines is one of the most important conditions that determine their reliability and level of flight safety. Unstable operation of the compressor in the engine system (surge) leads to loss of thrust accompanied by an increase in gas temperature in front of the turbine and increased vibration because of large amplitudes of pressure pulsations and mass flow through the engine path. To improve the parameters of ACS aviation gas turbine engines are increasingly using regulators built using fuzzy logic algorithms. The implementation of fuzzy control algorithms differs from classical algorithms, which are based on the concept of feedback and reproduce a given functional dependence or differential equation. These functions are related to the qualitative assessment of system behavior, analysis of the current changing situation, and the selection of the most appropriate for the situation supervision of the gas turbine engine. This concept is called advanced management. ACS gas turbine engines with fuzzy regulators are nonlinear systems in which stable self-oscillations are possible. Approximate methods are used to solve the problems of analysis of periodic oscillations in nonlinear systems. Among them, the most developed in theoretical and methodological aspects is the method of harmonic linearization. The scientific problem is solved in the work – methods of synthesis of intelligent control system with the fuzzy regulator as a separate subsystem based on the method of harmonic linearization and design on its basis of fuzzy ACS reserve of gas-dynamic stability of aviation gas turbine engine. Based on the analysis of the principles of construction of fuzzy control systems, it is shown that the use of fuzzy logic provides a new approach to the design of control systems for aviation gas turbine engines in contrast to traditional control methods. It is shown that the fuzzy controller, as the only essentially nonlinear element when using numerical integration methods, can be harmonically linearized. Harmonic linearization allows using the oscillation index to assess the quality in the separate channels of fuzzy ACS aviation gas turbine engines. A fuzzy expert system has been developed for optimal adjustment of the functions of belonging of typical fuzzy regulators according to quality criteria to transients.
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Myrhorod, Volodymyr, and Iryna Hvozdeva. "Методика наближеного синтезу регуляторів за умов забезпечення властивостей робастності." Aerospace Technic and Technology, no. 4sup1 (August 24, 2023): 58–63. http://dx.doi.org/10.32620/aktt.2023.4sup1.08.
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The subject of research – Methods, mathematical models, and methods of adjustment of regulators of automatic control systems with controlled changes in the state of power and energy installations based on gas turbine engines. The purpose of this study is to develop and apply a method of approximate synthesis of regulators with robustness properties, in particular, to the most important indicator of the quality of automatic control systems of gas turbine engines, namely stability reserves. The tasks faced by the developers consisted in analytically establishing the robustness conditions of gas turbine engine automatic control systems with respect to stability reserves, determining the possibilities of ensuring the established robustness conditions of gas turbine engine automatic control systems with respect to stability reserves using classical proportional-differential -integral regulators, conducting a computer experiment using a simplified model of a gas turbine engine and an automatic control system with a robust regulator, obtaining conditions and restrictions on the use of regulators with robustness properties. The methods that were used to achieve the established goal of the research: methods of modeling the controlled change in the state of power and energy installations based on gas turbine engines; methods of automatic control theory, in particular methods of sensitivity theory; and methods of conducting computer experiments. The results of the research constitute the proposed and mathematical modeling method of approximate synthesis of regulators possessing the properties of robustness, in particular, to the most important indicator of the quality of automatic control systems of gas turbine engines, namely stability reserves. The conditions and limitations of the fulfillment of the robustness conditions using classical proportional-differential-integral regulators are established. The scientific novelty of the obtained results lies in the fact that for the first time the issue of the sensitivity of stability and quality indicators of gas turbine engine automatic control systems to changes in object parameters was considered, and an approach was proposed to ensure the robustness of such systems with the help of appropriate settings of classical proportional-differential-integral regulators mode parameters of the object. The practical significance of the obtained results lies in the fact that the proposed technique allows finding a set of settings of proportional-differential-integral regulators of mode parameters by controlled change in the state of power and energy installations based on gas turbine engines, which ensure stabilization of sustainability indicators when the object parameters change.
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Li, Yi-Guang. "Diagnostics of power setting sensor fault of gas turbine engines using genetic algorithm." Aeronautical Journal 121, no. 1242 (July 3, 2017): 1109–30. http://dx.doi.org/10.1017/aer.2017.49.
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ABSTRACTGas path diagnostics is one of the most effective condition monitoring techniques in supporting condition-based maintenance of gas turbines and improving availability and reducing maintenance costs of the engines. The techniques can be applied to the health monitoring of different gas path components and also gas path measurement sensors. One of the most important measurement sensors is that for the engine control, also called the power setting sensor, which is used by the engine control system to control the operation of gas turbine engines. In most of the published research so far, it is rarely mentioned that faults in such sensors have been tackled in either engine control or condition monitoring. The reality is that if such a sensor degrades and has a noticeable bias, it will result in a shift in engine operating condition and misleading diagnostic results.In this paper, the phenomenon of a power-setting sensor fault has been discussed and a gas path diagnostic method based on a Genetic Algorithm (GA) has been proposed for the detection of power-setting sensor fault with and without the existence of engine component degradation and other gas path sensor faults. The developed method has been applied to the diagnostic analysis of a model aero turbofan engine in several case studies. The results show that the GA-based diagnostic method is able to detect and quantify the power-setting sensor fault effectively with the existence of single engine component degradation and single gas path sensor fault. An exceptional situation is that the power-setting sensor fault may not be distinguished from a component fault if both faults have the same fault signature. In addition, the measurement noise has small impact on prediction accuracy. As the GA-based method is computationally slow, it is only recommended for off-line applications. The introduced GA-based diagnostic method is generic so it can be applied to different gas turbine engines.
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Jafari, Soheil, and Theoklis Nikolaidis. "Turbojet Engine Industrial Min–Max Controller Performance Improvement Using Fuzzy Norms." Electronics 7, no. 11 (November 11, 2018): 314. http://dx.doi.org/10.3390/electronics7110314.
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The Min–Max control strategy is the most widely used control algorithm for gas turbine engines. This strategy uses minimum and maximum mathematical functions to select the winner of different transient engine control loops at any instantaneous time. This paper examines the potential of using fuzzy T and S norms in Min–Max selection strategy to improve the performance of the controller and the gas turbine engine dynamic behavior. For this purpose, different union and intersection fuzzy norms are used in control strategy instead of using minimum and maximum functions to investigate the impact of this idea in gas turbine engines controller design and optimization. A turbojet engine with an industrial Min–Max control strategy including steady-state and transient control loops is selected as the case study. Different T and S norms including standard, bounded, Einstein, algebraic, and Hamacher norms are considered to be used in control strategy to select the best transient control loop for the engine. Performance indices are defined as pilot command tracking as well as the engine response time. The simulation results confirm that using Einstein and Hamacher norms in the Min–Max selection strategy could enhance the tracking capability and the response time to the pilot command respectively. The limitations of the proposed method are also discussed and potential solutions for dealing with these challenges are proposed. The methodological approach presented in this research could be considered for enhancement of control systems in different types of gas turbine engines from practical point of view.
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Syaputra, Yudha, and Dewi Nusraningrum. "RAM Analysis at Gas Turbine Power Plant with Six Sigma Method." European Journal of Business and Management Research 7, no. 4 (August 29, 2022): 356–61. http://dx.doi.org/10.24018/ejbmr.2022.7.4.1609.
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The goal of this study is to identify breakdown that has an impact on the gas turbine engine's RAM and Six Sigma level in order to assess how well the gas turbine engine performance through the value of RAM (Reliability, Availability, and Maintainability) and Six Sigma. By gathering, compiling, categorizing, and conducting an analysis of data and information on the utilization of gas turbine engines, based on actual data and information, the descriptive analysis method is used to reveal the availability and performance of gas turbine engines. The findings of the RAM and Six Sigma level are examined utilizing the Pareto chart to identify the most impacted breakdown, the Fishbone diagram for root cause analysis, and the five why analysis approach for improvement suggestions. According to research findings, control system failure, VGV system failure, and load distribution problem have an impact on the RAM and Six Sigma level of two gas turbines. The Root cause of the issue is due to a number of factors, including mostly due to technical issues of unreliable old control system and VGV system design, an incorrect maintenance schedule implementation, an incompetent and ignorant of operator or technician to gas turbine engines.
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Peng, Kai, Ding Fan, Ran Ran Wu, and Yu Qiang Teng. "Active Predictive Control of Turbine Tip Clearance for Aero-Engine." Applied Mechanics and Materials 672-674 (October 2014): 1531–34. http://dx.doi.org/10.4028/www.scientific.net/amm.672-674.1531.
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Active control of turbine blade tip clearance continues to be a concern in design and control of gas turbines. Ever increasing demands for improved efficiency and higher operating temperatures require more stringent tolerances on turbine tip clearance. In this paper, a turbine tip clearance control apparatus and a model of turbine tip clearance are proposed. The active clearance control (ACC) of aero-engine turbine tip clearance is evaluated in a lapse-rate take-off transient, along with the comparative and quantitative analysis. The results show that the resultant active tip clearance control system has favorable steady-state and dynamic performance and benefits of increased efficiency, reduced specific fuel consumption, and additional service life.
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Matveenko, V., A. Dologlonyan, A. Klimenko, and V. Ocheretianyi. "OPERATION OF ELECTRIC HEAT-GENERATION GAS TURBINE PLANTS OF COMPLEX CYCLES ON NOMINAL AND VARIABLE MODES." National Association of Scientists 2, no. 37(64) (March 15, 2021): 17–22. http://dx.doi.org/10.31618/nas.2413-5291.2021.2.64.384.
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The results of research and development of cogeneration gas turbine engines (GTE) of complex cycles are presented. It is shown that the use of an overexpansion turbine (OT) in a gas turbine engine makes it possible to increase the efficiency of the engine on a par with the use of heat regeneration (R). The combination of these two methods in a GTE with OT and R provides a further increase in the engine's efficiency. It has been established that at partial loads, each design scheme has its own patterns of change in engine characteristics, which determine the field of application of cogeneration gas turbine engines. Examples of the possibilities of changing the working process in the engine are given, which allow to control the energy flows in the cogeneration power plant.
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Khizhnyakov, Yu N., A. A. Yuzhakov, S. A. Storozhev, and V. S. Nikulin. "Selective Control of a Gas-Turbine Engine." Russian Electrical Engineering 91, no. 11 (November 2020): 665–68. http://dx.doi.org/10.3103/s1068371220110073.
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Harrison, R. A., and M. S. Yates. "Gas Turbine Fuel Control Systems for Unmanned Applications." Journal of Engineering for Gas Turbines and Power 110, no. 1 (January 1, 1988): 33–40. http://dx.doi.org/10.1115/1.3240083.
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The technique of controlling engine acceleration has made possible gas turbine controls with simple hydromechanics and a minimal number of inputs into the electronics. This paper describes a control and electrical power generation system developed for an unmanned aircraft gas turbine, and the results obtained from the development engine running carried out with it.
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Castillo, Iván González, Igor Loboda, and Juan Luis Pérez Ruiz. "Data-Driven Models for Gas Turbine Online Diagnosis." Machines 9, no. 12 (December 20, 2021): 372. http://dx.doi.org/10.3390/machines9120372.
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The lack of gas turbine field data, especially faulty engine data, and the complexity of fault embedding into gas turbines on test benches cause difficulties in representing healthy and faulty engines in diagnostic algorithms. Instead, different gas turbine models are often used. The available models fall into two main categories: physics-based and data-driven. Given the models’ importance and necessity, a variety of simulation tools were developed with different levels of complexity, fidelity, accuracy, and computer performance requirements. Physics-based models constitute a diagnostic approach known as Gas Path Analysis (GPA). To compute fault parameters within GPA, this paper proposes to employ a nonlinear data-driven model and the theory of inverse problems. This will drastically simplify gas turbine diagnosis. To choose the best approximation technique of such a novel model, the paper employs polynomials and neural networks. The necessary data were generated in the GasTurb software for turboshaft and turbofan engines. These input data for creating a nonlinear data-driven model of fault parameters cover a total range of operating conditions and of possible performance losses of engine components. Multiple configurations of a multilayer perceptron network and polynomials are evaluated to find the best data-driven model configurations. The best perceptron-based and polynomial models are then compared. The accuracy achieved by the most adequate model variation confirms the viability of simple and accurate models for estimating gas turbine health conditions.
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Peng, Kai, Ding Fan, Lei Zhang, and Qiu Xia Wang. "A Novel Generalized Predictive Control and its Application on Active Clearance Control of Aero-Engine." Advanced Materials Research 616-618 (December 2012): 1922–25. http://dx.doi.org/10.4028/www.scientific.net/amr.616-618.1922.
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Turbine blade tip clearance continues to be a concern in the design and control of gas turbines. Ever increasing demands for improved efficiency and higher operating temperatures require more stringent tolerances on turbine tip clearance. An implicit active generalized predictive control with AR error modification and fuzzy adjustment on control horizon of aero-engine turbine tip clearance is presented and evaluated. The results show the resultant active tip clearance control system has good steady and dynamic performance and benefits of increased efficiency, reduced specific fuel consumption, and additional service life.
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Korczewski, Zbigniew. "Exhaust gas temperature measurements in diagnostic examination of naval gas turbine engines: Part II Unsteady processes." Polish Maritime Research 18, no. 3 (January 1, 2011): 37–42. http://dx.doi.org/10.2478/v10012-011-0015-x.
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Exhaust gas temperature measurements in diagnostic examination of naval gas turbine engines: Part II Unsteady processes The second part of the article presents the results of operating diagnostic tests of a two- and three-shaft engine with a separate power turbine during the start-up and acceleration of the rotor units. Attention was paid to key importance of the correctness of operation of the automatic engine load control system, the input for which, among other signals, is the rate of increase of the exhaust gas flow temperature. The article presents sample damages of the engine flow section which resulted from disturbed functioning of this system. The unsteady operation of the compressor during engine acceleration was the source of excessive increase of the exhaust gas temperature behind the combustion chamber and partial burning of the turbine blade tips.
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Tkachenko, Andrey, Viktor Rybakov, and Evgeny Filinov. "Distinctive Features of Altitude-velocity Characteristics of Detonation Gas Turbine Engines." MATEC Web of Conferences 220 (2018): 03008. http://dx.doi.org/10.1051/matecconf/201822003008.
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The paper describes the distinctive features of the altitude-velocity characteristics of detonation gas turbine engines. The necessity of developing a new type of gas turbine engines is substantiated and the main features of detonation engines are described. The principal constructive scheme of detonation gas turbine engines is presented. Developed the one-dimensional mathematical model of detonation gas turbine engine. This model describes a working process in a gas generator and a traction module. Its verification with a real prototype is performed. A number of studies were carried out using the developed mathematical model. A comparison of the pulsating engine with the classic afterburner was performed. From the obtained results it is concluded that detonation engines are more economical than the engines of traditional schemes. It was also revealed that it is possible to obtain a range of flight speeds depending on a certain height only by adjusting the gas generator according to different control laws. In this regard, the purpose of further work will be the development of a three-dimensional mathematical model of the detonation engine and the creation on its basis of a stand of virtual tests for further research.
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Catana, Razvan Marius, and Gabriel Petre Badea. "Experimental Analysis on the Operating Line of Two Gas Turbine Engines by Testing with Different Exhaust Nozzle Geometries." Energies 16, no. 15 (July 26, 2023): 5627. http://dx.doi.org/10.3390/en16155627.
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This paper presents a special analysis study about the gas turbine operating line, and an overall description of a gas turbines project, based on experimental data from two particular applications, in order to convert two different types of aero engines into the same engine configuration. The experimental works were carried out with the aim of converting an Ivchenko AI-20K turboprop and a Rolls-Royce Viper 632-41 turbojet into free turbine turboshaft engines, to be used in marine propulsion, and also to obtain an experimental database to be used in other gas turbine applications. In order to carry out the experimental work, the engines were tested in turbojet configuration, to simulate the free turbine load by using jet nozzles with different geometries of the outlet cross-section. Following the engines’ tests, a series of measured data were obtained, through which it was possible to experimentally determine the operating line of some engine components such as the compressor, turbine, and exhaust jet nozzle. This paper is comprehensive and useful through its scientific and technical guidelines, the operation curves coming in handy in the thermodynamic analysis and testing methodology for researchers dealing with similar applications.
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Tarasenko, O. I., A. O. Tarasenko, M. Radchenko, I. C. Scurtu, O. N. Volintiru, and V. Sichko. "Digital regulation of gas turbine engine on start modes." IOP Conference Series: Earth and Environmental Science 968, no. 1 (January 1, 2022): 012009. http://dx.doi.org/10.1088/1755-1315/968/1/012009.
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Abstract A gas turbine engine (GTE) with a free power turbine driven by an electric generator is considered. The GTE has an automatic computerized control system (ACS). The fuel for the gas turbine engine is natural gas. The fuel dosage is managed by computer in the moment of ignition, during the start and the idle operation of gas turbine engine.
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Nikolaidis, Theoklis, Zhuo Li, and Soheil Jafari. "Advanced Constraints Management Strategy for Real-Time Optimization of Gas Turbine Engine Transient Performance." Applied Sciences 9, no. 24 (December 6, 2019): 5333. http://dx.doi.org/10.3390/app9245333.
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Motivated by the growing technology of control and data processing as well as the increasingly complex designs of the new generation of gas turbine engines, a fully automatic control strategy that is capable of dealing with different aspects of operational and safety considerations is required to be implemented on gas turbine engines. An advanced practical control mode satisfaction method for the entire operating envelope of gas turbine engines is proposed in this paper to achieve the optimal transient performance for the engine. A constraint management strategy is developed to generate different controller settings for short-range fighters as well as long-range intercontinental aircraft engines at different operating conditions by utilizing a model predictive control approach. Then, the designed controller is tuned and modified with respect to different realistic considerations including the practicality, physical limitations, system dynamics, and computational efforts. The simulation results from a verified two-spool turbofan engine model and controller show that the proposed method is capable of maneuverability and/or fuel economy optimization indices while satisfying all the predefined constraints successfully. Based on the parameters, natural frequencies, and dynamic behavior of the system, a set of optimized weighting factors for different engine parameters is also proposed to achieve the optimal and safe operation for the engine at different flight conditions. The paper demonstrates the effects of the prediction length and control horizon; adding new constraints on the computational effort and the controller performance are also discussed in detail to confirm the effectiveness and practicality of the proposed approach in developing a fully automatic optimized real-time controller for gas turbine engines.
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Korczewski, Zbigniew. "Exhaust gas temperature measurements in diagnostic examination of naval gas turbine engines." Polish Maritime Research 18, no. 4 (January 1, 2011): 49–53. http://dx.doi.org/10.2478/v10012-011-0026-7.
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Exhaust gas temperature measurements in diagnostic examination of naval gas turbine engines The third part of the article presents a method for detecting failures of the automatic engine control system with the aid of an exhaust gas temperature setter, specially designed and machined for this purpose. It also presents a procedure of identifying the operating tolerances and determining the diagnostic tolerances for the exhaust gas temperature recorded in the naval turbine engine during the start-up and acceleration processes. The diagnostic tolerances were determined using the statistic inference, based on the hypothesis about the normal distribution of the starting exhaust gas temperature dispersion at the initial time of engine operation. The above hypothesis was verified using the non-parametric statistic test χ2 for examining the consistency of the empirical distribution with the assumed normal distribution. As a result of the examination, satisfactory convergence of the compared distributions was obtained which made the basis for assuming the three-sigma limits of the diagnostic tolerance for the analysed engine control parameter.
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Watts, J. W., T. E. Dwan, and C. G. Brockus. "Optimal State-Space Control of a Gas Turbine Engine." Journal of Engineering for Gas Turbines and Power 114, no. 4 (October 1, 1992): 763–67. http://dx.doi.org/10.1115/1.2906654.
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An analog fuel control for a gas turbine engine was compared with several state-space derived fuel controls. A single-spool, simple cycle gas turbine engine was modeled using ACSL (high level simulation language based on FORTRAN). The model included an analog fuel control representative of existing commercial fuel controls. The ACSL model was stripped of nonessential states to produce an eight-state linear state-space model of the engine. The A, B, and C matrices, derived from rated operating conditions, were used to obtain feedback control gains by the following methods: (1) state feedback; (2) LQR theory; (3) Bellman method; and (4) polygonal search. An off-load transient followed by an on-load transient was run for each of these fuel controls. The transient curves obtained were used to compare the state-space fuel controls with the analog fuel control. The state-space fuel controls did better than the analog control.
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Ashley, Steven. "Fuel-Saving Warship Drives." Mechanical Engineering 120, no. 08 (August 1, 1998): 63–67. http://dx.doi.org/10.1115/1.1998-aug-4.
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This article focuses on a fuel-efficient gas turbine engine featuring intercooling and heat recuperation, which is being developed to power a new generation of warships. Modern warships are often powered by gas turbine engines so they can take advantage of the turbine’s rapid response capabilities, solid operational reliability, high power density, and compact dimensions. For medium-size surface combatants such as destroyers, aircraft-derivative gas turbines have become the dominant propulsion engine type, having largely replaced traditional steam or diesel power plants. Though the all-electric concept is far from new, having been applied previously to merchant vessels, the technology is looking better of late. The NRC panel stated that gas turbine propulsion units, modular rare-earth permanent magnetic motors, and power control module technologies have matured to the point that all-electric ships appear feasible. The technology cited “unique advantages” in reduced volume, modular flexible propulsion, lower acoustic signature, enhanced survivability, high propeller torque at low speed, and inherent reversing capability. The result would be a submarine-type propulsion design with diesel-like fuel consumption.
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Meier, E., and J. Czerwinski. "Turbocharging Systems With Control Intervention for Medium Speed Four-Stroke Diesel Engines." Journal of Engineering for Gas Turbines and Power 111, no. 3 (July 1, 1989): 560–69. http://dx.doi.org/10.1115/1.3240291.
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The turbocharging systems of highly boosted four-stroke diesel engines (BMEP 25 bar/363 psi) have to cope with two basic problems: lack of air and compressor surge at reduced engine speed. In the case of medium speed engines for ship propulsion and stationary applications, the following three control interventions have proved to be successful solutions: (1) waste gating air or exhaust gas at full load and speed, (2) using a compounded or independent exhaust gas driven power turbine that can be shut off at part load and speed, and (3) blowing air from the compressor outlet to the turbine inlet through a controlled bypass. The effect of these control interventions on engine performance is shown by examples and analyzed by means of characteristic quantities for the efficiency of the turbocharging system and the engine. The definitions and meanings of these quantities are explained in the first part of the paper.
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Perez, R. A. "Model Reference Control of a Gas Turbine Engine." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 210, no. 4 (October 1996): 291–96. http://dx.doi.org/10.1243/pime_proc_1996_210_374_02.
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A simple control law is developed that guarantees that the outputs of a linear time invariant plant with feedthrough elements will converge asymptotically to a pre-specified set of desired trajectories. This control law is illustrated on a gas turbine engine to demonstrate its applicability to higher dimensional problems and to highlight the fast asymptotic convergence towards the desired trajectories. The algorithm presented here is fairly straightforward to implement, and should be a useful tool for model reference control. The desired model is implemented off-line, thus allowing for a potential real-time application. The only assumption made in this work is that the modes of the ‘actual’ plant are controllable. No assumptions are made or required on the ‘desired’ plant. The dynamic characteristics of both the ‘actual’ and the ‘desired’ plant can actually be quite different. The control law generates an input that forces the ‘actual’ outputs to follow the ‘desired’ trajectories.
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Singh, Richa, Arnab Maity, and P. S. V. Nataraj. "Shaft Speed Control of Laboratory Gas Turbine Engine." IFAC-PapersOnLine 52, no. 12 (2019): 262–67. http://dx.doi.org/10.1016/j.ifacol.2019.11.253.
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Langston, Lee S. "Blade Tips - Clearance and Its Control." Mechanical Engineering 135, no. 08 (August 1, 2013): 66–71. http://dx.doi.org/10.1115/1.2013-aug-4.
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This article focuses on studying blade tip clearance phenomena. It is important to realize that to be freely turning, a blade (or a cantilevered stator) must have a clearance gap between its tip and the engine casing (or hub). Such clearances introduce aerodynamic losses, decreasing gas turbine efficiency. Tip leakage losses in compressors can be significant and have been reviewed by the experts. During transient operations, gas turbine blade tip clearances will change based on blade/disk centrifugal loads and the different response times of engine parts to thermally induced expansions and contractions. Designers have perfected active clearance control (ACC) systems to deal with these transient conditions. ACC uses cool or hot gas path and fan air at appropriate times during transients to control the rate of expansion or contraction of internal parts adjacent to the gas path and outer casings. The research shows that continued enhancement of blade tip clearance management systems over a range of engine operating conditions has brought and will bring about gains in gas turbine efficiency.
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Tovkach, Serhii. "Закони керування авіаційним газотурбінним двигуном з турбовентиляторною приставкою." Aerospace Technic and Technology, no. 4sup1 (August 24, 2023): 70–74. http://dx.doi.org/10.32620/aktt.2023.4sup1.10.
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The main aspects of the general task of integrating an aviation engine (AE) with a turbofan additional unit (TAU) of a multi-mode aircraft are the selection of the scheme and design parameters of the AE with the TAU (including parameters of the work process), as well as methods and means of automatic control of the AE with the TAU for better matching its characteristics with certain flight modes. These two tasks are closely interrelated: on the one hand, when determining the appearance of the aircraft and its power plant (PP), it is necessary to consider what means will ensure the adaptation of its characteristics to the variable flight mode, and on the other hand, the purpose of the aircraft, its parameters and parameters of the PP, and the flight modes mostly determine the choice of control laws. The subject of the research is the formation of the laws of control of the aviation gas turbine engine with TAU. The goal is to improve the dynamic characteristics of the aviation gas turbine engine by applying adaptive control of the gas turbine engine with the use of wireless information exchange technologies. Objectives: to generalize the concept of adaptive control at the stage of determining the appearance of an engine with TAU; to determine the methods of regulating the GTE with TAU and their influence on the speed characteristics; to describe the process of formation of the laws governing AE with TAU; to investigate thermal processes in order to find functional dependencies in the optimal control of gas turbines with TAU. Research methods: system analysis, mathematical and computer modeling were used in the formation of control laws; the methods of philosophical knowledge were used to build an approach to the design of adaptive control systems of gas turbines with TAU. The theory of aircraft engines, the theory of differential equations, difference grids, and numerical methods were used to optimize the control of gas turbines with TAU. Results: methods of regulating the GTE with TAU and their influence on the speed characteristics of the aviation engine; formulas for researching the thermal processes of the working blades of the GTE with TAU in order to form the influence of the regulator on the executive mechanisms. Scientific and practical novelty: formation of a paradigm for the development of models of adaptive control of GTE with TAU, considering different flight modes of the aircraft and engine operation modes. The selection of control laws using multi-parameter optimization methods for finding the relationship between structural and component schemes of the gas generator and turbofan additional unit. The character of the engine thrust change depending on the input temperature is shown, which in turn, will allow to increase the efficiency of the fan and obtain a thrust reserve. The research directions of the temperature field and stress field were formed.
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Sankar, Balaji, Brijeshkumar Jayesh Shah, Soumendu Jana, R. K. Satpathy, and Gantayata Gouda. "Modeling of Degradation in Gas Turbine Engine by Modified Off Design Simulation." Defence Science Journal 72, no. 2 (May 11, 2022): 135–45. http://dx.doi.org/10.14429/dsj.72.15428.
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Legacy turbojet engines suffer degradation in performance with usage. Degradations in engine components show different observable symptoms based on the control mode of the engine. Hence, to accurately model the engine and its degradations, a novel off-design modeling method that considers the control settings of the engine is presented. The improvement in degradation modeling due to the modified scheme is presented in detail. The mathematical model used in the degradation simulation is validated by comparing the model outputs to the engine mounted sensor measurements at various ratings in the engine test bed. The estimation component parameters used in the model through nonlinear gas path analysis and optimisation-based routines is also presented.
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Volponi, A. J. "Gas Turbine Parameter Corrections." Journal of Engineering for Gas Turbines and Power 121, no. 4 (October 1, 1999): 613–21. http://dx.doi.org/10.1115/1.2818516.
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The various parameters appearing along an engine’s gas path, such as flows, pressures, temperatures, speeds, etc., not only vary with power condition but also with the ambient conditions at the engine’s inlet. Since a change in inlet temperature and/or pressure will contribute to an attendant change in a gas path parameter’s value, it would be difficult to characterize the aero-thermodynamic relationships between gas turbine engine parameters, (even at a constant engine operating point) unless the ambient conditions are somehow accounted for. This is usually accomplished through the use of corrected engine parameters. Although most of these corrections are well known by practitioners in the industry, knowledge of their origin does not appear to be as commonplace. The purpose of this paper is to fill that gap and furnish a summary of the commonly used corrections for the “major” gas path parameters that are used in performance analysis, diagnostics, and control design, and to offer a derivation of these corrections. We will suggest both an analytic approach as well as an empirical approach. The latter can be used to establish the correction for parameters not directly addressed in this paper, as well as to fine tune the correction factors when actual engine data is available.
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Vattanapuripakorn, Wenich, Khomson Khannam, Sathapon Sonsupap, Prachakon Kaewkhiaw, Umakorn Tongsantia, Jiradanai Sarasamkan, and Bopit Bubphachot. "Advanced Power Generation Using a Nitrogen Turbine Engine Instead of a Conventional Injection Steam Turbine Engine." Inventions 6, no. 4 (September 29, 2021): 62. http://dx.doi.org/10.3390/inventions6040062.
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An ever-increasing demand for electrical power and soaring levels of energy consumption around the world have led to an energy crisis. Thus, this paper aims to review the conventional technologies against those of newer developments in electrical power generation such as using nitrogen generators. The nitrogen generator method is most appealing as it is a seemingly free energy already existing in nature. A nitrogen generator with a 5000 (Nm3/h) capacity has the potential to be used to analyze gas composition and the results are compared with the gas composition of a conventional steam turbine, which is used to pressurize 6000 (kWh) injection steam turbines. The magnetic bearing must be installed in both systems to modify all centrifuged systems which reduces all energy consumption in all systems by more than 50%. Artificial intelligence is used with the machine to analyze and control nitrogen gas flow to provide a more precise evaluation resulting in a more efficient technology. It should further be noted that the nitrogen turbine is superior to the steam turbine because it does not require the burning of fossil fuel to generate power. Hence, it is crucial to modify conventional technologies to improve energy sustainability and begin the long task of tackling environmental issues.
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Song, Kang, Devesh Upadhyay, and Hui Xie. "A physics-based turbocharger model for automotive diesel engine control applications." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 233, no. 7 (May 19, 2018): 1667–86. http://dx.doi.org/10.1177/0954407018770569.
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Control-oriented models of turbocharger processes such as the compressor mass flow rate, the compressor power, and the variable geometry turbine power are presented. In a departure from approaches that rely on ad hoc empirical relationships and/or supplier provided performance maps, models based on turbomachinery physics and known geometries are attempted. The compressor power model is developed using Euler’s equations of turbomachinery, where the gas velocity exiting the rotor is estimated from an empirically identified correlation for the ratio between the radial and tangential components of the gas velocity. The compressor mass flow rate is modeled based on mass conservation, by approximating the compressor as an adiabatic converging-diverging nozzle with compressible fluid driven by external work input from the compressor wheel. The variable geometry turbine power is developed with Euler’s equations, where the turbine exit swirl and the gas acceleration in the vaneless space are neglected. The gas flow direction into the turbine rotor is assumed to align with the orientation of the variable geometry turbine vane. The gas exit velocity is calculated, similar to the compressor, based on an empirical model for the ratio between the turbine rotor inlet and exit velocities. A power loss model is also proposed that allows proper accounting of power transfer between the turbine and compressor. Model validation against experimental data is presented.
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Zhang,, Huisheng, Ming Su, and, and Shilie Weng. "Hardware-in-the-Loop Simulation Study on the Fuel Control Strategy of a Gas Turbine Engine." Journal of Engineering for Gas Turbines and Power 127, no. 3 (June 24, 2005): 693–95. http://dx.doi.org/10.1115/1.1805012.
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A hardware-in-the-loop simulation of a three-shaft gas turbine engine for ship propulsion was established. This system is composed of computers, actual hardware, measuring instruments, interfaces between actual hardware and computers, and a network for communication, as well as the relevant software, including mathematical models of the gas turbine engine. “Hardware-in-the-loop” and “volume inertia effects” are the two innovative features of this simulation system. In comparison to traditional methods for gas turbine simulation, the new simulation platform can be implemented in real time and also can test the physical hardware’s performance through their integration with the mathematical simulation model. A fuel control strategy for a three-shaft gas turbine engine, which can meet the requirement to the acceleration time and not exceeding surge line, was developed using this platform.
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Catana, R. M., G. Cican, and G. Dediu. "Gas Turbine Engine Starting Applicated on TV2-117 Turboshaft." Engineering, Technology & Applied Science Research 7, no. 5 (October 19, 2017): 2005–9. http://dx.doi.org/10.48084/etasr.1315.
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The paper presents the examination of two different types of engine starting configurations, applicated on TV2-117A turboshaft, running into the test bench. The first type of starting configuration is a normal starting, with the engine connected to the dynamometer which controls the free turbine speed by the dynamometer load. The second type of starting is a different one, the engine is not connected with the dynamometer, therefore it results that there is no control of the free turbine speed from the dynamometer, only from the engine but in particular conditions. To achieve the starting phase an instrumentation scheme is created, to control and monitor the engine, and a starting sequence with all the parameters, confirmations and commands that are involved into the starting phase. The engine starting is performed by the test bench operating system, composed of an acquisition system and a programmable controller, wherewith is running the starting sequence.
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Silva, Valceres V. R., Wael Khatib, and Peter J. Fleming. "Performance optimization of gas turbine engine." Engineering Applications of Artificial Intelligence 18, no. 5 (August 2005): 575–83. http://dx.doi.org/10.1016/j.engappai.2005.01.001.
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Sun, Xiaohuan, Soheil Jafari, Seyed Alireza Miran Fashandi, and Theoklis Nikolaidis. "Compressor Degradation Management Strategies for Gas Turbine Aero-Engine Controller Design." Energies 14, no. 18 (September 10, 2021): 5711. http://dx.doi.org/10.3390/en14185711.
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The Advisory Council for Aeronautics Research in Europe (ACARE) Flight Path 2050 focuses on ambitious and severe targets for the next generation of air travel systems (e.g., 75% reduction in CO2 emissions per passenger kilometre, a 90% reduction in NOx emissions, and a 65% reduction in the noise emissions of flying aircraft relative to the capabilities of typical new aircraft in 2000). Degradation is an inevitable phenomenon as aero-engines age with significant impacts on the engine performance, emissions level, and fuel consumption. The engine control system is a key element capable of coping with degradation consequences subject to the implementation of an advanced management strategy. This paper demonstrates a methodological approach for aero-engine controller adjustment to deal with degradation implications, such as emission levels and increased fuel consumption. For this purpose, a component level model for an aero-engine was first built and transformed to a block-structured Wiener model using a system identification approach. An industrial Min-Max control strategy was then developed to satisfy the steady state and transient limit protection requirements simultaneously while satisfying the physical limitation control modes, such as over-speed, surge, and over-temperature. Next, the effects of degradation on the engine performance and associated changes to the controller were analysed thoroughly to propose practical degradation management strategies based on a comprehensive scientometric analysis of the topic. The simulation results show that the proposed strategy was effective in restoring the degraded engine performance to the level of the clean engine while protecting the engine from physical limitations. The proposed adjustments in the control strategy reduced the fuel consumption and, as a result, the emission level and carbon footprint of the engine.
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Murugan, Muthuvel, Michael Walock, Anindya Ghoshal, Robert Knapp, and Roger Caesley. "Embedded Temperature Sensor Evaluations for Turbomachinery Component Health Monitoring." Energies 14, no. 4 (February 6, 2021): 852. http://dx.doi.org/10.3390/en14040852.
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Current rotorcraft gas turbine engines typically use titanium alloys and steel for the compressor section and single-crystal nickel superalloys for the hot-section turbine stator vanes and rotor blades. However, these material selections are rapidly changing due to increased requirements of power-density and efficiency. Future U.S. Army gas turbine engines will be using ceramic matrix composites for many high temperature engine components due to their low density and improved durability in high temperature environments. The gas turbine industry is also actively developing adaptive concept technologies for production and assembly of modular gas turbine engine components with integrated sensing. In order to actively monitor engine components for extended seamless operation and improved reliability, it is essential to have intelligent embedded sensing to monitor the health of critical components in engines. Under this U.S. Army Foreign Technology Assessment Support (FTAS) program funded research project, embedded fiber-optic temperature sensors from U.K.-based company, Epsilon Optics Ltd (Fordingbridge, UK)., were experimentally evaluated to measure temperature responses on typical turbomachinery component material coupons. The temperature responses from this foreign technology sensor were assessed using a thermomechanical fatigue tester with a built-in furnace to conduct thermal cycling durability experiments. The experimental results obtained from the durability performance of this embedded fiber Bragg sensor are reported in this paper. This sensor technology, upon maturation to higher TRL (technology readiness level), can greatly reduce the lifecycle cost of future U.S. Army gas turbine engines.
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Hoshino, A., T. Sugimoto, T. Tatsumi, and Y. Nakagawa. "Development of a 30PS Class Small Gas Turbine and Its Power-Up Version." Journal of Engineering for Gas Turbines and Power 111, no. 2 (April 1, 1989): 225–31. http://dx.doi.org/10.1115/1.3240240.
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Due to the recent popularity of small and medium-sized industrial gas turbines in many fields, gas turbines below 100 SHP have been employed as prime movers, a power range traditionally reserved for diesel and gasoline engines. Generally speaking, however, small gas turbines have many design difficulties in thermal efficiency, high rotational speed, compact auxiliary equipment, etc., derived from limitations of their dimensions. Small gas turbines S5A-01 and S5B-01, which have 32 PS output power at standard conditions, have been developed and are being produced. Presently, a 30 percent growth rated power producer for S5A-02 and S5B-02 gas turbines is under development. These engines’ configurations are as follows: single-stage centrifugal compressor; single-stage radial turbine; single can combustor; hybrid fuel nozzle with pressure atomizer and airblast atomizer; fuel control valve with pulse width modulation system; electric motor drive fuel pump. In this paper, the authors describe the design features and development history of the base engine and the experimental results with the growth rated version.
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Kuz’michev, Venedikt, Ilia Krupenich, Evgeny Filinov, and Andrey Tkachenko. "Optimization of gas turbine engine control using dynamic programming." MATEC Web of Conferences 220 (2018): 03002. http://dx.doi.org/10.1051/matecconf/201822003002.
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The aim of engine control optimization is to derive the optimal control law for engine operation managing during the aircraft flight. For numerical modeling a continuous flight process defined by a system of differential equations is replaced by a discrete multi-step process. Values of engine control parameters in particular step uniquely identify a system transitions from one state to another. The algorithm is based on the numerical method of dynamic programming and the Bellman optimality principle. The task is represented as a sequence of nested optimization subtasks, so that control optimization at the first step is external to all others. The optimum control function can be determined using the minimax principle of optimality. Aircraft performance calculation is performed by numerical integration of differential equations of aircraft movement.
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Valeev, Sagit, and Natalya Kondratyeva. "Life Test Optimization for Gas Turbine Engine Based on Life Cycle Information Support and Modeling." Energies 15, no. 19 (September 20, 2022): 6874. http://dx.doi.org/10.3390/en15196874.
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The task of choosing the modes and duration of life tests of complex technical objects, such as aircraft engines, is a complex and difficult-to-formalize task. Experimental optimization of the parameters of life tests of complex technical objects is costly in terms of material and time resources, which makes such an approach to the choice of test parameters practically difficult. The problem of life test optimization for gas turbine engines on the basis of the engine life cycle information support and statistical modeling is discussed. Within the framework of the research, the features of the optimization of life tests based on simulation modeling of the life cycle of gas turbine engines were studied. The criterion of the efficiency of the life tests was introduced, and this characterized the predicted effect (technical and economic) of the operation of a batch of engines, the reliability of which was confirmed by life tests; a method of complex optimization of resource tests in the life cycle system was developed. An objective function was formed for the complex optimization of life tests based on life cycle simulation. The principles of formation and refinement of the simulation model of the life cycle for the optimization of life tests were determined. A simulation model of the main stages of the life cycle of an auxiliary gas turbine engine was developed. A study was performed on the influence of the quality of the production of “critical” engine elements, the system of engine acceptance and shipment, as well as the effect of a range of parameters of the engine loading mode on the efficiency of the life tests of an auxiliary gas turbine engine. The optimal parameters of periodic life tests of an auxiliary gas turbine engine were determined by simulation modeling in the life cycle system, which made it possible to increase the equivalence of tests by several times and reduce their duration in comparison with the program of serial tests.
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Balicki, Włodzimierz, Paweł Głowacki, Stefan Szczecinski, Ryszard Chachurski, and Jerzy Szczeciński. "Effect of the Atmosphere on the Performances of Aviation Turbine Engines." Acta Mechanica et Automatica 8, no. 2 (August 15, 2014): 70–73. http://dx.doi.org/10.2478/ama-2014-0012.
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Abstract The paper presents how the parameters defining the state of the atmosphere: pressure, temperature, humidity, are affecting performance of the aircraft turbine engines and their durability. Also negative impact of dust pollution level is considered as an important source of engine deterioration. Article highlights limitation of the aircraft takeoff weight (TOW) and requirements for length of the runways depending on weather condition changes. These problems stem from the growing “demand” of gas turbine engines for an air. The highest thrust engines have air mass flow more than 1000 kg/s. Engine inlet ice formation is presented as a result of weather conditions and inlet duct design features.
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Thompson, H. A., and P. J. Fleming. "Fault-tolerant transputer arrays for gas turbine engine control." Computing & Control Engineering Journal 2, no. 5 (1991): 217. http://dx.doi.org/10.1049/cce:19910059.
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Shutler, A. G. "Control configuration design for the aircraft gas turbine engine." Computing & Control Engineering Journal 6, no. 1 (February 1, 1995): 22–28. http://dx.doi.org/10.1049/cce:19950109.
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